US3139725A - Steerable solid propellant rocket motor - Google Patents
Steerable solid propellant rocket motor Download PDFInfo
- Publication number
- US3139725A US3139725A US180382A US18038261A US3139725A US 3139725 A US3139725 A US 3139725A US 180382 A US180382 A US 180382A US 18038261 A US18038261 A US 18038261A US 3139725 A US3139725 A US 3139725A
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- Prior art keywords
- main nozzle
- propellant
- rocket motor
- skirt
- ducts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
Definitions
- This invention relates to steerable solid propellant rocket motors and included in the objects of this invention are:
- a steerable solid propellant rocket motor which is provided with laterally directed steering nozzles connected with the rocket motor chamber, and provided with valve means arranged for remote control so that laterally directed thrusts of selected duration may be made during operation of the rocket motor to guide the rocket motor and vehicle attached thereto.
- a steerable solid propellant rocket motor having a propellant chamber of essentially spherical form and provided with a main nozzle extending partly into the propellant chamber, and tour equally spaced laterally directed steering nozzles clustered around the outwardly projecting portion of the main nozzle and connec'ted with the propellant chamber by ducts terminating adjacent the main nozzle, the solid propellant being cast in the propellant chamber so as to clear the portion of the main nozzle therein and expose the entrance ends of the ducts so that pressure for steering control is available the instant pressure develops in the propellant chamber.
- a steerable rocket motor which is particularly adapted for use as the final stage or intermediate stage of a multiple stage rocket to effect orientation of the rocket payload, or as a retro-rocket to reduce velocity of the rocket vehicle.
- FIGURE 1 is a reduced fragmentary view of a multiple stage rocket motor showing the steerable rocket motor forming a part of the final stage.
- FIGURE 2 is an enlarged fragmentary sectional view of the steerable rocket motor taken substantially through 2-2 of FTGURE 3.
- FIGURE 3 is a longitudinal sectional view of the steerable rocket motor with the remaining portions of the final stage unit omitted.
- the steerable rocket motor includes a propellant chamber body l, which is illustrated as being spherical in form.
- the propellant chamber body is provided with a relatively large opening adapted to receive a main nozzle 2.
- the nozzle receiving opening is provided with an internally screw-threaded lip 3 which mates with a screw-threaded portion formed externally of the main nozzle 2.
- the main nozzle is in the form of a cone frustum with its smaller end directed into the chamber body and provided with a throat 4.
- the main nozzle is formed of metal whereas the throat is formed of graphite.
- the propellant chamber body is filled with a solid propellant charge 5 which has a central bore 6 coaxial with the main nozzle 2. That portion of the bore 6 which surrounds the nozzle 2 is spaced from and in parallelism with the walls of the nozzle to form an annular flow passage 7. Extending into the propellant charge bore 6 from the end thereof opposite from the main nozzle 2 is a standard igniter 8.
- chamber body 1 Adjacent the main nozzle supporting lip 3 the propellant 3,139,725 Patented July 7, 1964 chamber body 1 is provided with four laterally directed diverter ducts 9. The radially inner ends of these ducts project into the propellant charge 5 and terminate at the wall of the bore 6 so as to communicate with the flow passage 7.
- annular skirt 11 Secured to the propellant chamber body 1 is an annular skirt 11 which is in the form of a cone fustrum.
- the skirt is concentric with the main nozzle 2 and its walls converge from the propellant chamber body 1.
- Mounted in the walls of the skirt 11 in coaxial relation with the diverter ducts 9 are a set of tour guide rings 12.
- each diverter duct Mounted at the outer end of each diverter duct is a pair of complementary valve body members 13 and 14 which are joined together by bolts 15, and which are formed of heat-conducting, nonmetallic material.
- Each body member is provided with an inlet port 16 whereas each body member 1L is provided with a coaxial outlet port 17.
- the two body members form therebetween a valve chamber 1% which is spherical to receive a ball valve element 19 having a stem 20 and a bore or passageway 29 to permit the flow of propellant gases therethrough when the valve element is in its open position.
- Each valve body member 14 is provided with an integral steering nozzle 21 which diverges outwardly from the outlet port 7.
- the outer or discharge end of each steering nozzle extends into a corresponding guide ring 12 and externally is provided with a guide flange 22 which fits slidably within the guide ring 12 to permit thermal expansion of the nozzles.
- each ball valve element It! is connected by a coupling 23 to an armature 2dof a rotary solenoid contained in a housing which is secured to the skirt 11.
- the rotary solenoid is conventional and is the type which when energized turns Each ball valve is arranged to turn from its closed to its open position and from its open position to its closed position by a 90 rotation. Consequently, the rotary solenoid turns the corresponding valve element alternately between a closed and an open position.
- the propellant chamber body is provided with a suitable mounting ring 26 for attachment to the other portions of a final rocket stage 27 indicated diagrammatically in FIGURE 1.
- This rocket stage is connected in a conventional manner to a preceding rocket stage 28 and means not shown are employed to separate these stages in response to remote command or other signal.
- the rotary solenoids may be operated by remote command or may be operated by control devices carried by the rocket; for example, sensors which determine the course of the rocket motor and then operate the solenoids to open the steering nozzles for precise periods until the rocket motor is on course.
- the control afforded by the steering nozzles 21 and the rotary solenoids 2 5 are particularly adapted to permit use of the rocket motor as a retro rocket, that is, the steering nozzles may serve to cause the rocket motor to turn transverse to the axis of the main nozzle so that the thrust of the main nozzle may exert a retarding force to reduce the velocity of the rocket motor.
- a steerable solid propellant rocket motor comprlS- ing: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within saId skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; steering nozzles at the extremities of said diverter ducts having discharge ends penetrating the exterior surface of said skirt; valve means interposed in said ducts; and means for operating said valve means to effect selective operation of said steering nozzles.
- a steerable solid propellant rocket motor comprising: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within said skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; guide rings set in said skirt in coaxial relation with said ducts; steering nozzles having discharge ends slidable in said rings; valve means interposed between said steering nozzles and said ducts; and means for operating said valve means to eifect selective operation of said steering nozzles.
- a steerable solid propellant rocket motor comprising: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within said skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; a combination steering nozzle and valve means at the laterally outer end of each duct, each of said means including a valve body formed of a heat resisting non-metallic material defining a coaxial inlet, an outlet, and a valve chamber therebetween, said outlet having diverging walls forming said steering nozzle, and a rotary valve element journaled in said valve chamber; a guide ring for each steering nozzle set in said skirt to permit limiting sliding movement of said steering nozzle as said nozzle changes in temperature
- a steerable solid propellant rocket motor comprising:
- a steerable solid propellant rocket motor comprising:
- valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
- a steerable solid propellant rocket motor comprising:
- valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
- a steerable solid propellant rocket motor comprising:
- a steerable solid propellant rocket motor comprising:
- valve body having an integral steering nozzle gisposed at the radially outer end of each diverter
- valve body having an integral steering nozzle gisposed at the radially outer end of each diverter
- a steerable solid propellant rocket motor comprising:
- valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
Description
y 1964 JAMES E. WEBB 3,139,725
ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION STEERABLE SOLID PROPELLANT ROCKET MOTOR 2 Sheets-Sheet 1 Filed Oct. 51, 1961 f 1 INVENTOR.
142; 1 7/84 ac/o I/e BY (Q y 1964 JAMES E. WEBB 3,139,725
ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION STEERABLE SOLID PROPELLANT ROCKET MOTOR 2 Sheets-Sheet 2 Filed Oct. 31, 1961 IN-VENTOR. 614a W/aAcGm I/e ghwmww BY ,qrrae/viys United States Patent 3,139,725 STEERABLE SOLID PRGPELLANT RGCKET MOTOR James E. Webb, Administrator of the National Aeronautics and Space Administration, with respect to an invention of Earl W. Raggio, Jr.
Fiied Get. 31, 1961, Scr. No. 180,382 9 Claims. (Cl. 6tl35.4)
This invention relates to steerable solid propellant rocket motors and included in the objects of this invention are:
First, to provide a steerable solid propellant rocket motor which is provided with laterally directed steering nozzles connected with the rocket motor chamber, and provided with valve means arranged for remote control so that laterally directed thrusts of selected duration may be made during operation of the rocket motor to guide the rocket motor and vehicle attached thereto.
Second, to provide a steerable solid propellant rocket motor wherein the steering nozzles are provided with novel valve means adapted to withstand the heat generated by the combustion products of the solid propellant.
Third, to provide a steerable solid propellant rocket motor having a propellant chamber of essentially spherical form and provided with a main nozzle extending partly into the propellant chamber, and tour equally spaced laterally directed steering nozzles clustered around the outwardly projecting portion of the main nozzle and connec'ted with the propellant chamber by ducts terminating adjacent the main nozzle, the solid propellant being cast in the propellant chamber so as to clear the portion of the main nozzle therein and expose the entrance ends of the ducts so that pressure for steering control is available the instant pressure develops in the propellant chamber.
Fourth, to provide a steerable rocket motor which is particularly adapted for use as the final stage or intermediate stage of a multiple stage rocket to effect orientation of the rocket payload, or as a retro-rocket to reduce velocity of the rocket vehicle.
With the above and other objects in view as will appear hereinafter, reference is directed to the accompanying drawings in which:
FIGURE 1 is a reduced fragmentary view of a multiple stage rocket motor showing the steerable rocket motor forming a part of the final stage.
FIGURE 2 is an enlarged fragmentary sectional view of the steerable rocket motor taken substantially through 2-2 of FTGURE 3.
FIGURE 3 is a longitudinal sectional view of the steerable rocket motor with the remaining portions of the final stage unit omitted.
The steerable rocket motor includes a propellant chamber body l, which is illustrated as being spherical in form. The propellant chamber body is provided with a relatively large opening adapted to receive a main nozzle 2. The nozzle receiving opening is provided with an internally screw-threaded lip 3 which mates with a screw-threaded portion formed externally of the main nozzle 2.
The main nozzle is in the form of a cone frustum with its smaller end directed into the chamber body and provided with a throat 4. The main nozzle is formed of metal whereas the throat is formed of graphite.
The propellant chamber body is filled with a solid propellant charge 5 which has a central bore 6 coaxial with the main nozzle 2. That portion of the bore 6 which surrounds the nozzle 2 is spaced from and in parallelism with the walls of the nozzle to form an annular flow passage 7. Extending into the propellant charge bore 6 from the end thereof opposite from the main nozzle 2 is a standard igniter 8.
Adjacent the main nozzle supporting lip 3 the propellant 3,139,725 Patented July 7, 1964 chamber body 1 is provided with four laterally directed diverter ducts 9. The radially inner ends of these ducts project into the propellant charge 5 and terminate at the wall of the bore 6 so as to communicate with the flow passage 7.
Secured to the propellant chamber body 1 is an annular skirt 11 which is in the form of a cone fustrum. The skirt is concentric with the main nozzle 2 and its walls converge from the propellant chamber body 1. Mounted in the walls of the skirt 11 in coaxial relation with the diverter ducts 9 are a set of tour guide rings 12.
Mounted at the outer end of each diverter duct is a pair of complementary valve body members 13 and 14 which are joined together by bolts 15, and which are formed of heat-conducting, nonmetallic material. Each body member is provided with an inlet port 16 whereas each body member 1L is provided with a coaxial outlet port 17. The two body members form therebetween a valve chamber 1% which is spherical to receive a ball valve element 19 having a stem 20 and a bore or passageway 29 to permit the flow of propellant gases therethrough when the valve element is in its open position.
Each valve body member 14 is provided with an integral steering nozzle 21 which diverges outwardly from the outlet port 7. The outer or discharge end of each steering nozzle extends into a corresponding guide ring 12 and externally is provided with a guide flange 22 which fits slidably within the guide ring 12 to permit thermal expansion of the nozzles.
The stem fit of each ball valve element It! is connected by a coupling 23 to an armature 2dof a rotary solenoid contained in a housing which is secured to the skirt 11. The rotary solenoid is conventional and is the type which when energized turns Each ball valve is arranged to turn from its closed to its open position and from its open position to its closed position by a 90 rotation. Consequently, the rotary solenoid turns the corresponding valve element alternately between a closed and an open position.
The propellant chamber body is provided with a suitable mounting ring 26 for attachment to the other portions of a final rocket stage 27 indicated diagrammatically in FIGURE 1. This rocket stage is connected in a conventional manner to a preceding rocket stage 28 and means not shown are employed to separate these stages in response to remote command or other signal.
Operation of the steerable solid propellant rocket motor is as follows:
Upon i nition of the solid propellant charge 5 pressure rapidly builds up in the bore 6 of the propellant charge as the charge burns. The products of combustion discharge principally from the main nozzle 2. However, the ducts 9 are exposed to the pressures generated Within the propellant chamber body through the flow passage 7.
Four steering nozzles 21 are provided arranged 90 to each other. By momentarily opening the various associated valves lateral thrusts are applied to the rocket motor to change its course. The rotary solenoids may be operated by remote command or may be operated by control devices carried by the rocket; for example, sensors which determine the course of the rocket motor and then operate the solenoids to open the steering nozzles for precise periods until the rocket motor is on course.
The control afforded by the steering nozzles 21 and the rotary solenoids 2 5 are particularly adapted to permit use of the rocket motor as a retro rocket, that is, the steering nozzles may serve to cause the rocket motor to turn transverse to the axis of the main nozzle so that the thrust of the main nozzle may exert a retarding force to reduce the velocity of the rocket motor.
While what hereinbefore has been described as the preferred embodiment of this invention, it is readily apparent that alterations and modifications may be resorted to without departing from the scope of this invent1on and such alterations and modificaitons are intended to be included within the scope of the appended claims.
I-claim:
1. A steerable solid propellant rocket motor, comprlS- ing: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within saId skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; steering nozzles at the extremities of said diverter ducts having discharge ends penetrating the exterior surface of said skirt; valve means interposed in said ducts; and means for operating said valve means to effect selective operation of said steering nozzles.
2. A steerable solid propellant rocket motor, comprising: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within said skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; guide rings set in said skirt in coaxial relation with said ducts; steering nozzles having discharge ends slidable in said rings; valve means interposed between said steering nozzles and said ducts; and means for operating said valve means to eifect selective operation of said steering nozzles.
3. A steerable solid propellant rocket motor, comprising: a propellant chamber body of essentially spherical shape; a frusto conical skirt converging therefrom; a main nozzle diverging from said chamber within said skirt, said main nozzle having an inner portion extending into said body; a solid propellant charge initially filling said body and having a central bore receiving the inner portion of said main nozzle and spaced therefrom; a set of diverter ducts extending laterally from said body to said skirt and communicating with the bore of said propellant charge; a combination steering nozzle and valve means at the laterally outer end of each duct, each of said means including a valve body formed of a heat resisting non-metallic material defining a coaxial inlet, an outlet, and a valve chamber therebetween, said outlet having diverging walls forming said steering nozzle, and a rotary valve element journaled in said valve chamber; a guide ring for each steering nozzle set in said skirt to permit limiting sliding movement of said steering nozzle as said nozzle changes in temperature; and means for operating said valve means to effect selective operation of said steering nozzles.
4. A steerable solid propellant rocket motor, compris ing:
(a) a propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a main nozzle sealed in said opening and converging therefrom into said propellant chamber body and having a nozzle entrance at its inner end;
() a solid propellant within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) steering nozzles at the radially outer extremities of said diverter ducts;
(e) and remotely actuated valve means interposed in said diverter ducts.
5. A steerable solid propellant rocket motor, comprising:
(a) a propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a main nozzle sefled in said opening and converging therefrom into said propellant chamber body and having a nozzle entrance at its inner end;
(c) a solid propellant within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) a valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
(e) a valve in each valve body;
(f) and a rotary solenoid means for turning each valve.
6. A steerable solid propellant rocket motor, comprising:
(a) a propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a main nozzle sealed in said opening and converging therefrom into said propellant chamber body and having a nozzle entrance at its inner end;
(0) a solid propellant within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) a valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
(e) guide means supported from said propellant chamber body surrounding the radially outer ends of said steering nozzles to permit radial thermal expansion of said steering nozzles;
(f) a valve in each valve body;
(g) and a rotary solenoid means for turning each valve.
7. A steerable solid propellant rocket motor, comprising:
(a) a spherical propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a conical main nozzle sealed in said opening and having an entrance end at the center of said propellant chamber body;
(0) a solid propellant within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) steering nozzles at the radially outer extremities of said diverter ducts;
(e) and remotely actuated valve means interposed in said diverter ducts.
8. A steerable solid propellant rocket motor, comprising:
(a) a spherical propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a conical main nozzle sealed in said opening and having an entrance end at the center of said propellant chamber body;
(0) a solid propellant within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) a valve body having an integral steering nozzle gisposed at the radially outer end of each diverter (e) a valve in each valve body;
(1) and a rotary solenoid means for turning each valve.
9. A steerable solid propellant rocket motor, comprising:
(a) a spherical propellant chamber body having a main nozzle opening and a set of radiating diverter ducts adjacent said opening;
(b) a conical main nozzle sealed in said opening and having an entrance end at the center of said propellant chamber body;
(c) a solid propellant Within said propellant chamber body and surrounding said main nozzle, said propellant having a central bore coaxial with said main nozzle, and forming an annular passage externally of said main nozzle leading to said diverter ducts;
(d) a valve body having an integral steering nozzle disposed at the radially outer end of each diverter duct;
References Cited in the file of this patent UNITED STATES PATENTS Williamson et a1 Jan. 2, 1962 Hatfield Mar. 13, 1962 Rae July 24, 1962 FOREIGN PATENTS Germany Aug. 25, 1960
Claims (1)
1. A STEERABLE SOLID PROPELLANT ROCKET MOTOR, COMPRISING: A PROPELLANT CHAMBER BODY OF ESSENTIALLY SPHERICAL SHAPE: A FRUSTO CONICAL SKIRT CONVERGING THEREFROM; A MAIN NOZZLE DIVERGING FROM SAID CHAMBER WITHIN SAID SKIRT, SAID MAIN NOZZLE HAVING AN INNER PORTION EXTENDING INTO SAID BODY; A SOLID PROPELLANT CHARGE INITIALLY FILLING SAID BODY AND HAVING A CENTRAL BORE RECEIVING THE INNER PORTION OF SAID MAIN NOZZLE AND SPACED THEREFROM; A SET OF DIVERTER DUCTS EXTENDING LATERALLY FROM SAID BODY TO SAID SKIRT AND COMMUNICATING WITH THE BORE OF SAID PROPELLANT CHARGE; STEERING NOZZLES AT THE EXTREMITIES OF SAID DIVERTER DUCTS HAVING DISCHARGE ENDS PENETRATING THE EXTERIOR SURFACE OF SAID SKIRT; VALVE MEANS INTERPOSED IN SAID DUCTS; AND MEANS FOR OPERATING SAID VALVE MEANS TO EFFECT SELECTIVE OPERATION OF SAID STEERING NOZZLES.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US180382A US3139725A (en) | 1961-10-31 | 1961-10-31 | Steerable solid propellant rocket motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US180382A US3139725A (en) | 1961-10-31 | 1961-10-31 | Steerable solid propellant rocket motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3139725A true US3139725A (en) | 1964-07-07 |
Family
ID=22660255
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US180382A Expired - Lifetime US3139725A (en) | 1961-10-31 | 1961-10-31 | Steerable solid propellant rocket motor |
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| Country | Link |
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| US (1) | US3139725A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0078893A2 (en) * | 1981-11-10 | 1983-05-18 | Rheinmetall GmbH | Steerable projectile |
| US4392348A (en) * | 1981-08-05 | 1983-07-12 | The United States Of America As Represented By The Secretary Of The Army | Device for bleeding motor gases thru motor pole piece |
| US4522357A (en) * | 1983-01-19 | 1985-06-11 | Ford Aerospace & Communications Corp. | Ram air steering system for a guided missile |
| JPS60501366A (en) * | 1983-01-20 | 1985-08-22 | ローラル・エアロスペイス・コーポレイション | Ram air combustion steering system for guided missiles |
| US4550888A (en) * | 1977-10-11 | 1985-11-05 | Randle Douglass | Dual pressure solid propellant control system |
| EP0215185A1 (en) * | 1985-09-05 | 1987-03-25 | Rheinmetall GmbH | Steering block |
| US4685639A (en) * | 1985-12-23 | 1987-08-11 | Ford Aerospace & Communications Corp. | Pneumatically actuated ram air steering system for a guided missile |
| FR2684723A1 (en) * | 1991-12-10 | 1993-06-11 | Thomson Csf | Solid propergol-powered motor (thruster) with modifiable thrust and missile equipped |
| DE19735129C2 (en) * | 1996-08-14 | 2001-07-05 | Moog Inc | Hot gas control valve |
| US20050120703A1 (en) * | 2003-12-05 | 2005-06-09 | Rohrbaugh Eric M. | Steerable, intermittently operable rocket propulsion system |
| US20100192539A1 (en) * | 2006-03-02 | 2010-08-05 | Alliant Techsystems Inc. | Methods of controlling thrust in a rocket motor |
| CN103662094A (en) * | 2014-01-03 | 2014-03-26 | 中国人民解放军国防科学技术大学 | Inlaid type laminate side-spraying nose cone |
| US20160177873A1 (en) * | 2013-07-13 | 2016-06-23 | Mbda Uk Limited | A thrust flow powered vehicle |
| RU2709117C1 (en) * | 2018-12-26 | 2019-12-16 | Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") | Multiple inclusion solid propulsion systems and method of its multiple inclusion |
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| DE1087909B (en) * | 1958-11-18 | 1960-08-25 | Nord Aviation | Steering system for missiles with a combustion chamber for a fixed propellant |
| US3015210A (en) * | 1958-12-24 | 1962-01-02 | Bendix Corp | Attitude control for high altitude missile |
| US3024596A (en) * | 1955-03-16 | 1962-03-13 | Strato Missiles Inc | Propulsion system with automatic control of fuel and air |
| US3045596A (en) * | 1954-02-10 | 1962-07-24 | Randolph S Rae | Guided missile |
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1961
- 1961-10-31 US US180382A patent/US3139725A/en not_active Expired - Lifetime
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|---|---|---|---|---|
| US3045596A (en) * | 1954-02-10 | 1962-07-24 | Randolph S Rae | Guided missile |
| US3024596A (en) * | 1955-03-16 | 1962-03-13 | Strato Missiles Inc | Propulsion system with automatic control of fuel and air |
| DE1087909B (en) * | 1958-11-18 | 1960-08-25 | Nord Aviation | Steering system for missiles with a combustion chamber for a fixed propellant |
| US3015210A (en) * | 1958-12-24 | 1962-01-02 | Bendix Corp | Attitude control for high altitude missile |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4550888A (en) * | 1977-10-11 | 1985-11-05 | Randle Douglass | Dual pressure solid propellant control system |
| US4392348A (en) * | 1981-08-05 | 1983-07-12 | The United States Of America As Represented By The Secretary Of The Army | Device for bleeding motor gases thru motor pole piece |
| EP0078893A2 (en) * | 1981-11-10 | 1983-05-18 | Rheinmetall GmbH | Steerable projectile |
| EP0078893A3 (en) * | 1981-11-10 | 1983-12-14 | Rheinmetall Gmbh | Steerable projectile |
| US4541592A (en) * | 1981-11-10 | 1985-09-17 | Rheinmetall Gmbh. | Wing-stabilized projectile |
| US4522357A (en) * | 1983-01-19 | 1985-06-11 | Ford Aerospace & Communications Corp. | Ram air steering system for a guided missile |
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| US4573648A (en) * | 1983-01-20 | 1986-03-04 | Ford Aerospace And Communications Corp. | Ram air combustion steering system for a guided missile |
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